CN106828915A - A kind of tilted propeller can VTOL high-speed aircraft and its flight control method - Google Patents
A kind of tilted propeller can VTOL high-speed aircraft and its flight control method Download PDFInfo
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- CN106828915A CN106828915A CN201710152468.6A CN201710152468A CN106828915A CN 106828915 A CN106828915 A CN 106828915A CN 201710152468 A CN201710152468 A CN 201710152468A CN 106828915 A CN106828915 A CN 106828915A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8209—Electrically driven tail rotors
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Abstract
The present invention propose a kind of tilted propeller can VTOL high-speed aircraft and its flight control method, high-speed aircraft fuselage head is provided with canard, and the forward position of afterbody is provided with wing, and vertical fin is installed on afterbody top；Tilted propeller is arranged on arm outer end of verting；Two arms that vert are symmetrically mounted on the forward position both sides of waist, and the arm that verts can vert together with tilted propeller around arm axle line locking of verting；Tail-rotor is arranged on afterbody, is driven using separate electrical motor, and tail-rotor can be around fuselage datum deflection.Tilted propeller of the present invention is arranged on the waist position between canard and sweepforward host wing, in the VTOL stage, propeller downwash flow is without flow through any fixed aerofoil, do not block, on the one hand the hovering efficiency of full machine can be improved, on the other hand the aerodynamic interference between propeller downwash flow during verting and fixed aerofoil is also small, the smooth transition flown before being capable of achieving aircraft from VTOL to high speed, also reduces conversion flight control difficulty.
Description
Technical field
The present invention relates to aviation aircraft technical field, specially a kind of tilted propeller can VTOL high-speed flight
Device and its flight control method.
Background technology
U.S. V-22 " osprey " aircraft is a kind of typical tilt rotor aircraft, and the major diameter rotor of its wing both sides is hanging down
Pull-up aircraft during straight landing, while auto-bank unit manipulates rotor disk change control aircraft carries out pitching, rolling and driftage fortune
It is dynamic；Rotor is tilted forward with certain speed after taking off vertically, and aircraft accelerates, and last aircraft is changed into the propeller that both sides rotor is pulled
Fixed wing aircraft carries out high-speed flight.Tiltrotor is turned to using rotor and used as propeller, improves the flight of helicopter
Speed, is to develop to obtain high-speed helicopter the most ripe so far, and " osprey " aircraft also has been enter into United States Forces' military service.But
It is that " osprey " aircraft is not flawless, the important shortcoming of one is that rotor is arranged in wing two ends, in VTOL rank
Section wing forms larger area and blocks to rotor downwash, reduces the hovering efficiency of aircraft；In addition verted in rotor
During, complicated aerodynamic interference has also heightened the difficulty of process flight control of verting between rotor downwash and wing.Pin
To this shortcoming of " osprey ", also there is engineer to propose to be designed to together be verted with rotor by the outer section of wing, reduce under rotor
Gas washing stream is blocked, but this design can improve the hovering efficiency of aircraft, but does not reduce pneumatic dry during verting
Disturb, and the part that verts increases the increase that will also result in inclining rotary mechanism weight.
The content of the invention
To solve the problems, such as prior art, there is provided a kind of tilted propeller with the interference of low rotorwash can be vertical
The high-speed aircraft of landing, the present invention propose a kind of tilted propeller can VTOL high-speed aircraft and its flight controlling party
Method.
The technical scheme is that：
A kind of tilted propeller can VTOL high-speed aircraft, including fuselage, wing, vertical fin, peace in fuselage
Equipped with engine and transmission system；It is characterized in that：Fuselage head is provided with canard, and canard is arranged using lower single-blade, with preceding
Edge angle of sweep；The forward position of afterbody is provided with wing, and wing is arranged and with leading edge sweepforward angle using high mounted wing；Vertical fin is pacified
Loaded on afterbody top, with leading edge sweep；
The high-speed aircraft also includes two arms that vert, two tilted propellers and a tail-rotors；The arm that verts is to incline
The supporting mechanism of rotating propeller, tilted propeller is arranged on arm outer end of verting；Arm section vert for spindle, arm lengths of verting are big
In the radius of tilted propeller, axis is parallel with body axis system OY axles, and it is forward that two arms that vert are symmetrically mounted on waist
Position both sides, between canard and wing, the arm that verts can vert together with tilted propeller around arm axle line locking of verting；Two
Can tilted propeller can be counter-rotation through transmission system drives by engine, tail-rotor be arranged on afterbody, using independent electricity
Machine drives, and tail-rotor rotation axis is parallel with body axis system OYZ planes, produces upward pulling force, and tail-rotor can be vertical around fuselage
Axle deflection.
Further preferred scheme, a kind of tilted propeller can VTOL high-speed aircraft, it is characterised in that：
The fuselage cross-section is the square of four rounding of angle, and fuselage head and afterbody shrink to form nose cone and tail cone.
A kind of tilted propeller can VTOL high-speed aircraft control method, it is characterised in that：
When taking off, can tilted propeller be tilted to Plane of rotation and body axis system OXY plane parallel positions, tail-rotor
In Plane of rotation and body axis system OXY plane parallel positions, engine driving can tilted propeller rotation, motor driving tail
Oar rotates, can tilted propeller and tail-rotor produce pulling force needed for VTOL, aircraft vertical to take off；
In take-off process, by change both sides can tilted propeller pitch, formed pulling force difference and around the rolling of center of gravity
Torque, carries out the rolling control of aircraft；By changing the pitch of tail-rotor, realize changing the upward pulling force of tail-rotor generation and around center of gravity
Pitching moment size, carry out the pitch control of aircraft；Deflected around fuselage datum by by tail-rotor, form horizontal component, carried out
The driftage control of aircraft；
After aircraft is liftoff reaches safe altitude, control can tilted propeller tilt forward, form horizontal pull forward,
Aircraft starts flight forward, and canard and wing produce lift, into transfer process；With can tilted propeller tilt forward angle
Increase, horizontal pull increase forward, the increase of aircraft forward flight speed, canard and wing produce lift increase；When aircraft accelerates to reach
To and more than after conversion speed, transfer process is completed, and can tilted propeller be tilted to Plane of rotation and put down with body axis system OYZ
Face is parallel, and the pulling force of horizontal flight, tail-rotor stalling, into fixed-wing offline mode, by canard, wing and vertical fin are provided completely
On control rudder face carry out aspect control；
When aircraft needs landing, control can tilted propeller reduction forward flight speed, when forward flight speed, to be reduced to certain big
When the setting value of conversion speed, tail-rotor start rotation, control can tilted propeller vert upwards, forward flight speed further drops
It is low, by canard and airfoil lift, can tilted propeller pulling force upward component and tail-rotor pulling force keep aircraft vertical direction to draw
Power；When can tilted propeller vert to Plane of rotation and body axis system OXY plane parallel positions, forward flight speed is reduced to 0, enters
Enter the vertical landing stage；
In the vertical landing stage, by change both sides can tilted propeller pitch, form pulling force difference and around the rolling of center of gravity
Torque, carries out the rolling control of aircraft；By changing the pitch of tail-rotor, realize changing the upward pulling force of tail-rotor generation and around weight
The pitching moment size of the heart, carries out the pitch control of aircraft；Deflected around fuselage datum by by tail-rotor, form horizontal component, entered
The driftage control of row aircraft.
Beneficial effect
A kind of tilted propeller proposed by the present invention can VTOL high-speed aircraft, compared to U.S.'s V-22 types
Tiltrotor, because the tilted propeller for providing main lift and pulling force is arranged in the fuselage between canard and sweepforward host wing
Portion position, in the VTOL stage, propeller downwash flow is not blocked without flow through any fixed aerofoil, and this aspect can be with
The hovering efficiency of full machine is improved, on the other hand the aerodynamic interference between propeller downwash flow during verting and fixed aerofoil
Also smooth transition that is small, flying before being capable of achieving aircraft from VTOL to high speed, also reduces conversion flight control difficulty.
Additionally, the spiral that can vert only needs to carry out always adjusted away from change in the VTOL stage carries out flight control process
Pulling force size, and without carrying out vertical and horizontal feathering regulation as rotor, control structure is compared to relatively simple.Using
Tail-rotor and propeller provide VTOL pulling force jointly, and center of gravity is located between propeller and tail-rotor, and center of gravity mobile range is gone straight up to
Machine and tiltrotor are also big, so as to facilitate fuselage load arrangement.
Additional aspect of the invention and advantage will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by practice of the invention.
Brief description of the drawings
Of the invention above-mentioned and/or additional aspect and advantage will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Fig. 1：The structural perspective of VTOL state of the present invention
Fig. 2：The structural perspective of winged state preceding at a high speed of the invention
Wherein：1st, canard；2nd, fuselage；3rd, tilted propeller；4th, wing；5th, deflectable tail-rotor；6th, vertical tail；7th, vert
Arm.
Specific embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from start to finish
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
It is exemplary to scheme the embodiment of description, it is intended to for explaining the present invention, and be not considered as limiting the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", D score, "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are, based on orientation shown in the drawings or position relationship, to be for only for ease of
The description present invention is described with simplified, must have specific orientation, Yi Te rather than the device or element for indicating or imply meaning
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
The present embodiment be a frame tilted propeller can VTOL high-speed unmanned aerial vehicle, the design maximum take-off weight of aircraft
It is 340kg, it is the turbo oar engine of 100kw to use a peak power；The conversion speed for setting is 50m/s, transition status
Flying height is 500m.The tilted propeller can VTOL high-speed aircraft, using canard forward-swept-wing configuration, including duck
The wing, wing, fuselage, vertical fin, the arm that verts, can tilted propeller and deflectable tail-rotor.
Fuselage cross-section is the square of four rounding of angle, and head and afterbody shrink to form more sharp nose cone and tail cone, to subtract
Small flight resistance.Turboshaft engine, operating mechanism, fuel oil box, mission payload and necessary flight instrumentation are installed in fuselage to set
Standby etc., fuselage length is 4.5m, and Breadth Maximum is 0.6m, and maximum height is 0.5m.
Canard is installed on fuselage head, forms lower single-blade arrangement, and trailing edge is disposed with elevator, and the span is 2.5m, root chord length
0.48m, slightly chord length 0.24m, leading edge sweep are 10.8 °, and the upper counterangle is 0 °, and torsion angle is 0 °.
Wing is installed on the forward position of afterbody, high mounted wing arrangement is formed, when being aircraft fixed-wing mode flight
Mainpiston, span 6m, slightly root chord length 0.9m, chord length 0.42m, leading edge sweepforward angle are 8 °, and the upper counterangle is 0 °, and torsion angle is 0 °,
Ending arranges the aileron by carrying out rolling control.
The wing that hangs down is arranged on fuselage afterbody top, mainly plays course stability action, wing root chord length 0.88m, wingtip chord length
0.44m, 0.63m high, 40 ° of leading edge sweep, the wing afterbody that hangs down are provided with rudder.
Two arms that vert be can tilted propeller supporting mechanism, its section is the spindle of big thickness, and length is more than inclining
The radius of rotating propeller, axis is parallel with OY axles (body axis system OXYZ is American-European coordinate system), is symmetrically mounted on waist
Forward position, between canard and wing, can synchronize with tilted propeller and vert.Two can tilted propeller installation
It is six leaf oars at the two ends for verting arm, with pitch-setting mechanism, oar disk diameter 1.2m, rotation axis is symmetrically put down apart from fuselage
Face 0.95m, propeller and the arm that verts synchronously can be verted between 0 ° and 90 °, so that propeller is providing VTOL
Changed between lift and horizontal flight pulling force.Two can tilted propeller it is counter-rotation through transmission system drives by engine, from
And offset driving torque；In aircraft vertical landing, can tilted propeller Plane of rotation it is parallel with OXY planes, its pulling force use
In the gravity for overcoming aircraft；When aircraft cruises as fixed-wing, propeller Plane of rotation goes to, its drawing parallel with OYZ planes
Power is used to provide thrust when flying before aircraft；In changeover portion, propeller around vert arm axle line between 0 degree to 90 degree (definition with
It is 0 degree that Plane of rotation is parallel with OYZ planes, and parallel with OXY planes is 90 degree) rotation；Propeller now both provides a part
Lift, provides a part of thrust again.
Deflectable tail-rotor is arranged on afterbody, and separate electrical motor drives, and rotation axis is parallel with OYZ planes, produces upward
Pulling force.Deflectable tail-rotor is four leaf oars, and with pitch-setting mechanism, a diameter of 0.3m of oar disk can be around fuselage datum or so partially
Turn 10 °, so as to form certain horizontal pull, and then the yawing around center of gravity is formed to fuselage, enter in the VTOL stage
The yawing rotation control of row aircraft.
The flight course and control method of aircraft be：
When taking off, can tilted propeller be tilted to Plane of rotation and body axis system OXY plane parallel positions, tail-rotor
In Plane of rotation and body axis system OXY plane parallel positions, engine driving can tilted propeller rotation, motor driving tail
Oar rotates, can tilted propeller rotation increases pitch and produces pulling force needed for most of VTOL, afterbody tail-rotor to produce simultaneously at a high speed
Raw remaining required pulling force, aircraft vertical takes off.
In take-off process, by change both sides can tilted propeller pitch, formed pulling force difference and around the rolling of center of gravity
Torque, carries out the rolling control of aircraft；By changing the pitch of tail-rotor, realize changing the upward pulling force of tail-rotor generation and around center of gravity
Pitching moment size, carry out the pitch control of aircraft；Deflected around fuselage datum by by tail-rotor, form horizontal component, carried out
The driftage control of aircraft.
After aircraft is liftoff reaches safe altitude, control can tilted propeller tilt forward, form horizontal pull forward,
Aircraft starts flight forward, and canard and wing produce lift, into transfer process；With can tilted propeller tilt forward angle
Increase, horizontal pull increase forward, the increase of aircraft forward flight speed, canard and wing produce lift increase；When aircraft accelerates to reach
To and more than after conversion speed, transfer process is completed, and can tilted propeller be tilted to Plane of rotation and put down with body axis system OYZ
Face is parallel, and the pulling force of horizontal flight is provided completely, and tail-rotor is stalled, and into fixed-wing offline mode, canard and wing can be produced
Whole lift and controling power needed for aircraft controllable flight, aircraft appearance is carried out by the control rudder face on canard, wing and vertical fin
State is controlled.
When aircraft needs landing, control can tilted propeller reduction forward flight speed, when forward flight speed, to be reduced to certain big
When the setting value of conversion speed, tail-rotor start rotation, control can tilted propeller vert upwards, forward flight speed further drops
It is low, by canard and airfoil lift, can tilted propeller pulling force upward component and tail-rotor pulling force keep aircraft vertical direction to draw
Power；When can tilted propeller vert to Plane of rotation and body axis system OXY plane parallel positions, forward flight speed is reduced to 0, enters
Enter the vertical landing stage.
In the vertical landing stage, by change both sides can tilted propeller pitch, form pulling force difference and around the rolling of center of gravity
Torque, carries out the rolling control of aircraft；By changing the pitch of tail-rotor, realize changing the upward pulling force of tail-rotor generation and around weight
The pitching moment size of the heart, carries out the pitch control of aircraft；Deflected around fuselage datum by by tail-rotor, form horizontal component, entered
The driftage control of row aircraft.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from principle of the invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (3)
1. a kind of tilted propeller can VTOL high-speed aircraft, including fuselage, wing, vertical fin are provided with hair in fuselage
Motivation and transmission system；It is characterized in that：Fuselage head is provided with canard, and canard is arranged using lower single-blade, with leading-edge sweep
Angle；The forward position of afterbody is provided with wing, and wing is arranged and with leading edge sweepforward angle using high mounted wing；Vertical fin is installed on machine
Body upper rear, with leading edge sweep；
The high-speed aircraft also includes two arms that vert, two tilted propellers and a tail-rotors；The arm that verts is the spiral shell that can vert
The supporting mechanism of oar is revolved, tilted propeller is arranged on arm outer end of verting；Arm section vert for spindle, arm lengths of verting are more than inclines
The radius of rotating propeller, axis is parallel with body axis system OY axles, and two arms that vert are symmetrically mounted on the forward position of waist
Both sides, between canard and wing, the arm that verts can vert together with tilted propeller around arm axle line locking of verting；Two can incline
Rotating propeller can be counter-rotation through transmission system drives by engine, and tail-rotor is arranged on afterbody, is driven using separate electrical motor
Dynamic, tail-rotor rotation axis is parallel with body axis system OYZ planes, produces upward pulling force, and tail-rotor can be left around fuselage datum
Right avertence turns.
2. according to claim 1 a kind of tilted propeller can VTOL high-speed aircraft, it is characterised in that：The machine
Body section is the square of four rounding of angle, and fuselage head and afterbody shrink to form nose cone and tail cone.
3. a kind of tilted propeller can VTOL high-speed aircraft control method, it is characterised in that：
When taking off, can tilted propeller be tilted to Plane of rotation and body axis system OXY plane parallel positions, tail-rotor is in
Plane of rotation and body axis system OXY plane parallel positions, engine driving can tilted propeller rotations, motor driving tail-rotor rotation
Turn, can tilted propeller and tail-rotor produce pulling force needed for VTOL, aircraft vertical to take off；
In take-off process, by change both sides can tilted propeller pitch, formed pulling force difference and around the rolling moment of center of gravity,
Carry out the rolling control of aircraft；By changing the pitch of tail-rotor, realize changing upward pulling force and the bowing around center of gravity that tail-rotor is produced
Torque size is faced upward, the pitch control of aircraft is carried out；Deflected around fuselage datum by by tail-rotor, form horizontal component, carry out aircraft
Driftage control；
After aircraft is liftoff reaches safe altitude, control can tilted propeller tilt forward, form horizontal pull forward, aircraft
Start flight forward, canard and wing produce lift, into transfer process；With can tilted propeller tilt forward angle increase
Greatly, horizontal pull increase forward, the increase of aircraft forward flight speed, canard and wing produce lift increase；When aircraft accelerates to reach
After more than conversion speed, transfer process is completed, and can tilted propeller be tilted to Plane of rotation and body axis system OYZ planes
It is parallel, the pulling force of horizontal flight, tail-rotor stalling, into fixed-wing offline mode, by canard, wing and vertical fin are provided completely
Control rudder face carry out aspect control；
When aircraft need landing when, control can tilted propeller reduction forward flight speed, when forward flight speed be reduced to certain more than turn
During the setting value of throw-over degree, tail-rotor start rotation, control can tilted propeller vert upwards, forward flight speed is further reduced, lead to
Cross canard and airfoil lift, can tilted propeller pulling force upward component and tail-rotor pulling force keep aircraft vertical direction pulling force；When
Can tilted propeller vert to Plane of rotation and body axis system OXY plane parallel positions, forward flight speed is reduced to 0, into hanging down
Straight landing period；
In the vertical landing stage, by change both sides can tilted propeller pitch, form pulling force difference and around the rolling power of center of gravity
Square, carries out the rolling control of aircraft；By changing the pitch of tail-rotor, realize changing the upward pulling force of tail-rotor generation and around center of gravity
Pitching moment size, carries out the pitch control of aircraft；Deflected around fuselage datum by by tail-rotor, form horizontal component, flown
The driftage control of machine.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710152468.6A CN106828915B (en) | 2017-03-15 | 2017-03-15 | Control method of high-speed aircraft with tilting propeller capable of vertically taking off and landing |
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| CN201710152468.6A CN106828915B (en) | 2017-03-15 | 2017-03-15 | Control method of high-speed aircraft with tilting propeller capable of vertically taking off and landing |
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